Device for pressurizing a propellant tank for a rocket motor

The device comprises a primary heater (58) adapted to heat the propellant from the reservoir (16) before its reintroduction in the tank. The primary heater uses the engine combustion heat (10) and the device further comprises a secondary reheater (66), the heat source is independent of the engine, the secondary heater being disposed downstream of the primary heater (58) to heat the propellant between its exit from the primary heater and its reintroduction into the tank. The device also comprises means (62) for pressurizing the propellant between the supply of the primary heater (58) and the return of the propellant to the reservoir.